Nothing Special   »   [go: up one dir, main page]

US3627443A - Turbine blade - Google Patents

Turbine blade Download PDF

Info

Publication number
US3627443A
US3627443A US854987A US3627443DA US3627443A US 3627443 A US3627443 A US 3627443A US 854987 A US854987 A US 854987A US 3627443D A US3627443D A US 3627443DA US 3627443 A US3627443 A US 3627443A
Authority
US
United States
Prior art keywords
blade
rib means
turbine blade
cooling
hollow
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US854987A
Inventor
Ludwig Pirzer
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Daimler Benz AG
Original Assignee
Daimler Benz AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Daimler Benz AG filed Critical Daimler Benz AG
Application granted granted Critical
Publication of US3627443A publication Critical patent/US3627443A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • B23P15/04—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/203—Heat transfer, e.g. cooling by transpiration cooling
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention relates to a turbine blade with convection-cooling or veil-cooling (transpiration cooling).
  • Such types of blades may be cast as hollow blades whereby a core consisting of ceramic material is subsequently etched out.
  • Such blades have become known in the prior art which are constructed of a solid blade core provided with grooves that is surrounded by a thin-walled casing or jacket. These prior art types of blades, however, require a certain minimum size for their manufacture. Below this minimum size only solid blades without these cooling possibilities could be made heretofore.
  • V I convection-cooling or veil-cooling
  • a particularly advantageous manufacture of two approximately equally large blade halves' can be achieved according to the present invention in that a connecting seam extending approximately in the profile center plane of the blade is extended on the baseplate of the bladebase parallel to the longitudinal axis thereof and passes over at its end faces into the center plane thereof.
  • Another object of the present invention resides in a turbine blade which is provided with cooling means regardless of the size of the blade.
  • Another object of the present invention resides in a turbine blade of hollow construction to permit cooling thereof which can be readily manufactured by simple means even for small blade sizes.
  • Still a further object of the present invention resides in a turbine blade with convectionor veil-cooling which can be manufactured also in very small dimensions.
  • FIG. I is a side view of a turbine blade in accordance with the present invention.
  • FIG. 2 is a perspective plan view of the turbine blade of FIG.
  • FIG. 3 is a longitudinal cross-sectional view taken along line Ill-Ill of FIG. 2;
  • FIG. 4 is a cross-sectional view taken along IV-IV ofFIG. l.
  • the turbine blade illustrated in the various figures is constructed as hollow blade which contains individual air-guide chambers 11, 12 and 13 (FIG. 4) which extend from the blade generally designated by reference numeral 14 to the blade base 15.
  • Inlet channels 16 (FIG. 3) which are arranged below the blade root 17 on each longitudinal side 18 of the blade base 15, serve for the supply of cooling air to the air-guide chambers 11, 12 and 13.
  • very small apertures 20 of different diameters for the air discharge are distributed over the entire outer surface 19 thereof, of which a few are illustrated in FIGS. 3 and 4.
  • the sievelike interrupted surface 19 enables the formation of an air-screen or air-veil which cools the thermally, highly loaded surface of the blade l4.
  • the turbine blade is welded together from two hollow blade halves 21 and 22 (FIGS. 3 and 4) made on precision castings.
  • the connecting seam 23 (FIGS. 1, 2 and 3) extends approximately in the profile center plane 24 of the blade 14 and is extended on the baseplate 25 parallel to the longitudinal axis 26 (FIG. 2) of the blade base 15. At the end faces 27 (FIG. 1) of the blade base 15, the connecting seam 23 passes over into the center plane thereof.
  • the hollow blade halves 21 and 22 are provided within the area of the blade 14 with essentially the same wall thickness.
  • Axial ribs 28, 29 and 30 and rib projections 31 form the air-guide chambers 11, 12 and 13 and further subdivide the same. Simultaneously, they reinforce the blade 14.
  • the ribs 30 starting from the hollow blade half 22 project beyond the profile center plane 24 into the other hollow blade half 21 and are welded into a continuous, uninterrupted separating wall together with the corresponding rib projections 31 at the hollow blade half 21.
  • the welding seams 32 start from the surface 19 of the hollow blade half 21 and extend from the rib projections 31 into the ribs 30 of the hollow blade half 22.
  • the hollow blade halves may also be manufactured according to any other known manufacturing methods. Prior to the connection of the blade halves already provided with cooling air apertures, possibly the interior walls and the connecting surface are machined accurately to exact dimensions. Electron beam welding is particularly suited for the connection. However, also other connecting methods, for example, soldering or brazing may be used. The blades may be subjected subsequently for the afterfinishing of the blade profile and of the shape of the blade base to a fine finishing operation, for exam ple, by eroding, etching or electrolytic grinding.
  • the particular advantage of the turbine blade according to the present invention resides in the fact that also blades with convection-cooling or veil-cooling (transpiration cooling) having very small dimensions can be manufactured.
  • the blade illustrated in the example has a height of about 25 mm. and a profile thickness of about 2 to 3 mm.
  • Such types of blades can be used not only as rotor blades but also as guide blades of turbines.
  • a turbine blade with convectionor transpiration-cooling characterized by two nondetachably connected blade halves which are provided with substantially axial, internal rib means, of which at least one rib means of one hollow blade half projects beyond the profile center plane into the other hollow blade half and is connected thereat with a corresponding other rib means, and a connecting seam connecting the external surfaces of the blade halves, said connecting seam extending approximately in the profile center plane of the blade and extending at the baseplate of the blade base parallel to the longitudinal axis of the blade base and passing over at its end faces into the center plane thereof.
  • a turbine blade according to claim 1 characterized in that the rib means form several individual cooling air chambers, of which at least the rib means connected together form a continuous, uninterrupted wall, said wall extending along the entire length of the respective rib means.
  • a turbine blade according to claim 2 characterized in that some of the manually opposite rib means terminate at a small distance from one another to form a gap therebetween, said gap extending along the entire length of the respective rib means and said gap adapted to permit air transfer to cooling chambers adjacent thereto.
  • nal rib means of which at least one rib means of one hollow blade half projects beyondthe profile center plane into the other hollow blade half and is connected thereat with a corresponding other rib means, characterized in that the rib means form several individual cooling inner chambers of which at least the rib means connected together form a continuous, uninterrupted wall, said wall extending along the en tire length of the respective rib means.
  • a turbine blade according to claim characterized in that some of the mutually opposite rib means terminate at a small distance from one another to form a gap therebetween.
  • a turbine blade according to claim 5 characterized in that the blade surfaces are provided with small discharge apertures to permit the discharge of the cooling air.
  • a turbine blade according to claim 5 characterized in that the rib-means comprising the walls are adapted to be welded together from the external surface of the blade.
  • a turbine blade according to claim 3. further characterized in that the gaps and walls are alternated within the blade.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Laser Beam Processing (AREA)
  • Electrical Discharge Machining, Electrochemical Machining, And Combined Machining (AREA)
  • Welding Or Cutting Using Electron Beams (AREA)

Abstract

A turbine blade with convection-cooling or screen-cooling which is capable of manufacture in small sizes and consists of two hollow blade halves provided with axial internal ribs, of which at least one rib of one hollow blade half extends beyond the profile center plane into the other hollow blade half and is connected thereat with a corresponding rib extension.

Description

United States Patent lnventor Ludwig Pirzer Vorst Bezirk Dusseldorf, Germany Appl. No. 854,987 Filed Sept. 3, 1969 Patented Dec. 14, 1971 Assignee Daimler-Benz Aktlengesellschaft Stuttgart-Unterturkheim, Germany Priority Sept. 4, 1968 Germany P 17 76 015.5
TURBINE BLADE 10 Claims, 4 Drawing Figs.
U.S. Cl 416/90, 416/97,4l6/233 Int. Cl Fold 5/18 Field 0: Search 416/90, 95, 96, 97, 231, 233, 92, 232, 233,415/115 References Cited UNITED STATES PATENTS 9/1957 Roush 416/90 X Primary Examiner-Everette A. Powell, Jr. Attorney-Craig, Antonelli, Stewart & Hill ABSTRACT: A turbine blade with convection-cooling or screen-cooling which is capable of manufacture in small sizes and consists of two hollow blade halves provided with axial internal ribs, of which at least one rib of one hollow blade half extends beyond the profile center plane into the other hollow blade half and is connected thereat with a corresponding rib extension.
PATENTEU DEC 1 4 IS'II SHEET 1 [1F 2 FIG. I
PATENTED 115mm 3 27L443 sum 2 or 2 INVENTOR LUDWIG PIRZER ATTORNEYS TURBINE BLADE The present invention relates to a turbine blade with convection-cooling or veil-cooling (transpiration cooling). Such types of blades may be cast as hollow blades whereby a core consisting of ceramic material is subsequently etched out. Also, such blades have become known in the prior art which are constructed of a solid blade core provided with grooves that is surrounded by a thin-walled casing or jacket. These prior art types of blades, however, require a certain minimum size for their manufacture. Below this minimum size only solid blades without these cooling possibilities could be made heretofore. V I
It is the aim of the present invention to eliminate this disadvantage and to create a turbine blade with convectionor veilcooling (transpiration cooling) which can also be manufactured in very small dimensions. This is realized according to the present invention by two hollow blade halves non detachably connected with each other which are provided with axial internal ribs, of which at least one rib of one hollow blade half projects beyond the profile center plane into the other hollow blade half and is connected thereat to a corresponding rib projection.
A particularly advantageous manufacture of two approximately equally large blade halves'can be achieved according to the present invention in that a connecting seam extending approximately in the profile center plane of the blade is extended on the baseplate of the bladebase parallel to the longitudinal axis thereof and passes over at its end faces into the center plane thereof.
Accordingly, it is an object of the present invention to provide a turbine blade which avoids by simple means, the aforementioned shortcomings and drawbacks encountered in the prior art.
Another object of the present invention resides in a turbine blade which is provided with cooling means regardless of the size of the blade.
Another object of the present invention resides in a turbine blade of hollow construction to permit cooling thereof which can be readily manufactured by simple means even for small blade sizes.
Still a further object of the present invention resides in a turbine blade with convectionor veil-cooling which can be manufactured also in very small dimensions.
These and further objects, features and advantages of the present invention will become more obvious from the following description when taken in connection with the accompanying drawing, which shows, for purposes of illustration only, one embodiment of a turbine blade on an enlarged scale of a jet-propulsion unit, and wherein:
FIG. I is a side view of a turbine blade in accordance with the present invention;
FIG. 2 is a perspective plan view of the turbine blade of FIG.
FIG. 3 is a longitudinal cross-sectional view taken along line Ill-Ill of FIG. 2; and
FIG. 4 is a cross-sectional view taken along IV-IV ofFIG. l.
Referring now to the drawing wherein like reference numerals are used throughout the various views to designate like parts, the turbine blade illustrated in the various figures is constructed as hollow blade which contains individual air-guide chambers 11, 12 and 13 (FIG. 4) which extend from the blade generally designated by reference numeral 14 to the blade base 15. Inlet channels 16 (FIG. 3) which are arranged below the blade root 17 on each longitudinal side 18 of the blade base 15, serve for the supply of cooling air to the air-guide chambers 11, 12 and 13. Corresponding to the temperature profile of the blade 14, very small apertures 20 of different diameters for the air discharge are distributed over the entire outer surface 19 thereof, of which a few are illustrated in FIGS. 3 and 4. The sievelike interrupted surface 19 enables the formation of an air-screen or air-veil which cools the thermally, highly loaded surface of the blade l4.
The turbine blade is welded together from two hollow blade halves 21 and 22 (FIGS. 3 and 4) made on precision castings. The connecting seam 23 (FIGS. 1, 2 and 3) extends approximately in the profile center plane 24 of the blade 14 and is extended on the baseplate 25 parallel to the longitudinal axis 26 (FIG. 2) of the blade base 15. At the end faces 27 (FIG. 1) of the blade base 15, the connecting seam 23 passes over into the center plane thereof. The hollow blade halves 21 and 22 are provided within the area of the blade 14 with essentially the same wall thickness. Axial ribs 28, 29 and 30 and rib projections 31 form the air-guide chambers 11, 12 and 13 and further subdivide the same. Simultaneously, they reinforce the blade 14. The ribs 30 starting from the hollow blade half 22 project beyond the profile center plane 24 into the other hollow blade half 21 and are welded into a continuous, uninterrupted separating wall together with the corresponding rib projections 31 at the hollow blade half 21. The welding seams 32 (FIG. 4) start from the surface 19 of the hollow blade half 21 and extend from the rib projections 31 into the ribs 30 of the hollow blade half 22. The mutually opposite ribs 28 and 29 of the two hollow blade halves 21 and 22, in contradistinction thereto, leave open between the same a small gap 33 (FIGS. 3 and 4).
Instead of being made by precision casting, the hollow blade halves may also be manufactured according to any other known manufacturing methods. Prior to the connection of the blade halves already provided with cooling air apertures, possibly the interior walls and the connecting surface are machined accurately to exact dimensions. Electron beam welding is particularly suited for the connection. However, also other connecting methods, for example, soldering or brazing may be used. The blades may be subjected subsequently for the afterfinishing of the blade profile and of the shape of the blade base to a fine finishing operation, for exam ple, by eroding, etching or electrolytic grinding.
The particular advantage of the turbine blade according to the present invention resides in the fact that also blades with convection-cooling or veil-cooling (transpiration cooling) having very small dimensions can be manufactured. Thus, the blade illustrated in the example has a height of about 25 mm. and a profile thickness of about 2 to 3 mm.
Such types of blades can be used not only as rotor blades but also as guide blades of turbines.
While I have shown and described only one embodiment in accordance with the present invention, it is understood that the same is not limited thereto but is susceptible of numerous changes and modifications as known to a person skilled in the art, and I therefore do not wish to be limited to the details shown and described herein but intend to cover all such changes and modifications as known to those skilled in the art.
Iclaim:
l. A turbine blade with convectionor transpiration-cooling, characterized by two nondetachably connected blade halves which are provided with substantially axial, internal rib means, of which at least one rib means of one hollow blade half projects beyond the profile center plane into the other hollow blade half and is connected thereat with a corresponding other rib means, and a connecting seam connecting the external surfaces of the blade halves, said connecting seam extending approximately in the profile center plane of the blade and extending at the baseplate of the blade base parallel to the longitudinal axis of the blade base and passing over at its end faces into the center plane thereof.
2. A turbine blade according to claim 1, characterized in that the rib means form several individual cooling air chambers, of which at least the rib means connected together form a continuous, uninterrupted wall, said wall extending along the entire length of the respective rib means.
3. A turbine blade according to claim 2, characterized in that some of the manually opposite rib means terminate at a small distance from one another to form a gap therebetween, said gap extending along the entire length of the respective rib means and said gap adapted to permit air transfer to cooling chambers adjacent thereto.
nal rib means, of which at least one rib means of one hollow blade half projects beyondthe profile center plane into the other hollow blade half and is connected thereat with a corresponding other rib means, characterized in that the rib means form several individual cooling inner chambers of which at least the rib means connected together form a continuous, uninterrupted wall, said wall extending along the en tire length of the respective rib means.
' 6. A turbine blade according to claim characterized in that some of the mutually opposite rib means terminate at a small distance from one another to form a gap therebetween.
7. A turbine blade according to claim 5 characterized in that the blade surfaces are provided with small discharge apertures to permit the discharge of the cooling air.
8. A turbine blade according to claim 6. characterized in that the gaps and walls are alternated within the blade.
9. A turbine blade according to claim 5, characterized in that the rib-means comprising the walls are adapted to be welded together from the external surface of the blade.
10. A turbine blade according to claim 3. further characterized in that the gaps and walls are alternated within the blade.
i l I I

Claims (10)

1. A turbine blade with convection- or transpiration-cooling, cHaracterized by two nondetachably connected blade halves which are provided with substantially axial, internal rib means, of which at least one rib means of one hollow blade half projects beyond the profile center plane into the other hollow blade half and is connected thereat with a corresponding other rib means, and a connecting seam connecting the external surfaces of the blade halves, said connecting seam extending approximately in the profile center plane of the blade and extending at the base plate of the blade base parallel to the longitudinal axis of the blade base and passing over at its end faces into the center plane thereof.
2. A turbine blade according to claim 1, characterized in that the rib means form several individual cooling air chambers, of which at least the rib means connected together form a continuous, uninterrupted wall, said wall extending along the entire length of the respective rib means.
3. A turbine blade according to claim 2, characterized in that some of the manually opposite rib means terminate at a small distance from one another to form a gap therebetween, said gap extending along the entire length of the respective rib means and said gap adapted to permit air transfer to cooling chambers adjacent thereto.
4. A turbine blade according to claim 3, characterized in that the blade surfaces are provided with small discharge apertures to permit the discharge of the cooling air.
5. A turbine blade with convection- or transpiration-cooling, characterized by two nondetachably connected hollow blade halves which are provided with substantially axial, internal rib means, of which at least one rib means of one hollow blade half projects beyond the profile center plane into the other hollow blade half and is connected thereat with a corresponding other rib means, characterized in that the rib means form several individual cooling inner chambers of which at least the rib means connected together form a continuous, uninterrupted wall, said wall extending along the entire length of the respective rib means.
6. A turbine blade according to claim 5, characterized in that some of the mutually opposite rib means terminate at a small distance from one another to form a gap therebetween.
7. A turbine blade according to claim 5, characterized in that the blade surfaces are provided with small discharge apertures to permit the discharge of the cooling air.
8. A turbine blade according to claim 6, characterized in that the gaps and walls are alternated within the blade.
9. A turbine blade according to claim 5, characterized in that the rib means comprising the walls are adapted to be welded together from the external surface of the blade.
10. A turbine blade according to claim 3, further characterized in that the gaps and walls are alternated within the blade.
US854987A 1968-09-04 1969-09-03 Turbine blade Expired - Lifetime US3627443A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19681776015 DE1776015A1 (en) 1968-09-04 1968-09-04 Turbine blade

Publications (1)

Publication Number Publication Date
US3627443A true US3627443A (en) 1971-12-14

Family

ID=5702796

Family Applications (1)

Application Number Title Priority Date Filing Date
US854987A Expired - Lifetime US3627443A (en) 1968-09-04 1969-09-03 Turbine blade

Country Status (4)

Country Link
US (1) US3627443A (en)
DE (1) DE1776015A1 (en)
FR (1) FR2017340A1 (en)
GB (1) GB1233289A (en)

Cited By (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3810286A (en) * 1969-09-10 1974-05-14 Universal Cyclops Specialty St Methods for manufacturing hollow members
US3858290A (en) * 1972-11-21 1975-01-07 Avco Corp Method of making inserts for cooled turbine blades
US3932061A (en) * 1972-09-05 1976-01-13 General Motors Corporation Fluid unit rotor
US4211516A (en) * 1976-04-23 1980-07-08 Bbc Brown Boveri & Company Limited Blade structure for fluid flow rotary machine
US4286924A (en) * 1978-01-14 1981-09-01 Rolls-Royce Limited Rotor blade or stator vane for a gas turbine engine
US4472866A (en) * 1982-03-01 1984-09-25 Trw Inc. Method of making an airfoil
FR2559422A1 (en) * 1984-02-13 1985-08-16 Gen Electric COMPOSITE HOLLOW BLADE PROFILE ELEMENT WITH CORRUGATED INTERNAL SUPPORT STRUCTURE AND MANUFACTURING METHOD THEREOF
FR2559423A1 (en) * 1984-02-13 1985-08-16 Gen Electric COMPOSITE HOLLOW BLADE PROFILE ELEMENTS AND THEIR MANUFACTURING METHOD
US4583274A (en) * 1982-03-01 1986-04-22 Trw Inc. Method of making an airfoil
EP0194883A2 (en) * 1985-03-13 1986-09-17 Westinghouse Electric Corporation Fabricated blade with spanwise cooling passages for gas turbine
US5193975A (en) * 1990-04-11 1993-03-16 Rolls-Royce Plc Cooled gas turbine engine aerofoil
US5203873A (en) * 1991-08-29 1993-04-20 General Electric Company Turbine blade impingement baffle
US5391256A (en) * 1993-04-05 1995-02-21 General Electric Company Hollow airfoil cavity surface texture enhancement
US5431537A (en) * 1994-04-19 1995-07-11 United Technologies Corporation Cooled gas turbine blade
US5876183A (en) * 1995-11-11 1999-03-02 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh Blade for rotors and method for producing rotors with such blades
US6435825B1 (en) * 2001-04-10 2002-08-20 General Electric Company Hollow nozzle partition with optimized wall thickness and method of forming
US20070002686A1 (en) * 2005-06-30 2007-01-04 Spx Corporation Mixing impeller and method with top and bottom skin elements
US20090010765A1 (en) * 2007-07-06 2009-01-08 United Technologies Corporation Reinforced Airfoils
US20090060714A1 (en) * 2007-08-30 2009-03-05 General Electric Company Multi-part cast turbine engine component having an internal cooling channel and method of forming a multi-part cast turbine engine component
US20120121436A1 (en) * 2010-11-15 2012-05-17 Mtu Aero Engines Gmbh Rotor for a turbo machine
US20170074116A1 (en) * 2014-07-17 2017-03-16 United Technologies Corporation Method of creating heat transfer features in high temperature alloys
US10808547B2 (en) 2016-02-08 2020-10-20 General Electric Company Turbine engine airfoil with cooling

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE829969C (en) * 1943-02-27 1952-01-31 Maschf Augsburg Nuernberg Ag Hollow blade for impellers of centrifugal machines through which axial flow flows
FR1007303A (en) * 1949-08-24 1952-05-05 Improvements to rotor blades
DE758097C (en) * 1940-06-08 1954-02-22 Versuchsanstalt Fuer Luftfahrt Blade attachment for gas or exhaust turbine blades
US2807437A (en) * 1952-05-01 1957-09-24 Thompson Prod Inc Method for making intricate hollow powder metal parts
US2923525A (en) * 1958-04-04 1960-02-02 Orenda Engines Ltd Hollow gas turbine blade
US3017159A (en) * 1956-11-23 1962-01-16 Curtiss Wright Corp Hollow blade construction
US3468513A (en) * 1966-06-11 1969-09-23 Daimler Benz Ag Cooled rotor blade

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE758097C (en) * 1940-06-08 1954-02-22 Versuchsanstalt Fuer Luftfahrt Blade attachment for gas or exhaust turbine blades
DE829969C (en) * 1943-02-27 1952-01-31 Maschf Augsburg Nuernberg Ag Hollow blade for impellers of centrifugal machines through which axial flow flows
FR1007303A (en) * 1949-08-24 1952-05-05 Improvements to rotor blades
US2807437A (en) * 1952-05-01 1957-09-24 Thompson Prod Inc Method for making intricate hollow powder metal parts
US3017159A (en) * 1956-11-23 1962-01-16 Curtiss Wright Corp Hollow blade construction
US2923525A (en) * 1958-04-04 1960-02-02 Orenda Engines Ltd Hollow gas turbine blade
US3468513A (en) * 1966-06-11 1969-09-23 Daimler Benz Ag Cooled rotor blade

Cited By (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3810286A (en) * 1969-09-10 1974-05-14 Universal Cyclops Specialty St Methods for manufacturing hollow members
US3932061A (en) * 1972-09-05 1976-01-13 General Motors Corporation Fluid unit rotor
US3858290A (en) * 1972-11-21 1975-01-07 Avco Corp Method of making inserts for cooled turbine blades
US4211516A (en) * 1976-04-23 1980-07-08 Bbc Brown Boveri & Company Limited Blade structure for fluid flow rotary machine
US4286924A (en) * 1978-01-14 1981-09-01 Rolls-Royce Limited Rotor blade or stator vane for a gas turbine engine
US4472866A (en) * 1982-03-01 1984-09-25 Trw Inc. Method of making an airfoil
US4583274A (en) * 1982-03-01 1986-04-22 Trw Inc. Method of making an airfoil
FR2559422A1 (en) * 1984-02-13 1985-08-16 Gen Electric COMPOSITE HOLLOW BLADE PROFILE ELEMENT WITH CORRUGATED INTERNAL SUPPORT STRUCTURE AND MANUFACTURING METHOD THEREOF
FR2559423A1 (en) * 1984-02-13 1985-08-16 Gen Electric COMPOSITE HOLLOW BLADE PROFILE ELEMENTS AND THEIR MANUFACTURING METHOD
US4594761A (en) * 1984-02-13 1986-06-17 General Electric Company Method of fabricating hollow composite airfoils
EP0194883A2 (en) * 1985-03-13 1986-09-17 Westinghouse Electric Corporation Fabricated blade with spanwise cooling passages for gas turbine
EP0194883A3 (en) * 1985-03-13 1989-01-18 Westinghouse Electric Corporation Fabricated blade with spanwise cooling passages for gas turbine
US5193975A (en) * 1990-04-11 1993-03-16 Rolls-Royce Plc Cooled gas turbine engine aerofoil
US5203873A (en) * 1991-08-29 1993-04-20 General Electric Company Turbine blade impingement baffle
US5391256A (en) * 1993-04-05 1995-02-21 General Electric Company Hollow airfoil cavity surface texture enhancement
US5441574A (en) * 1993-04-05 1995-08-15 General Electric Company Hollow airfoil cavity surface texture enhancement
US5431537A (en) * 1994-04-19 1995-07-11 United Technologies Corporation Cooled gas turbine blade
US5876183A (en) * 1995-11-11 1999-03-02 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh Blade for rotors and method for producing rotors with such blades
US6435825B1 (en) * 2001-04-10 2002-08-20 General Electric Company Hollow nozzle partition with optimized wall thickness and method of forming
US20070002686A1 (en) * 2005-06-30 2007-01-04 Spx Corporation Mixing impeller and method with top and bottom skin elements
US20090010765A1 (en) * 2007-07-06 2009-01-08 United Technologies Corporation Reinforced Airfoils
US7857588B2 (en) * 2007-07-06 2010-12-28 United Technologies Corporation Reinforced airfoils
US20090060714A1 (en) * 2007-08-30 2009-03-05 General Electric Company Multi-part cast turbine engine component having an internal cooling channel and method of forming a multi-part cast turbine engine component
US20120121436A1 (en) * 2010-11-15 2012-05-17 Mtu Aero Engines Gmbh Rotor for a turbo machine
US9022727B2 (en) * 2010-11-15 2015-05-05 Mtu Aero Engines Gmbh Rotor for a turbo machine
US20170074116A1 (en) * 2014-07-17 2017-03-16 United Technologies Corporation Method of creating heat transfer features in high temperature alloys
US10808547B2 (en) 2016-02-08 2020-10-20 General Electric Company Turbine engine airfoil with cooling

Also Published As

Publication number Publication date
GB1233289A (en) 1971-05-26
DE1776015A1 (en) 1971-09-16
FR2017340A1 (en) 1970-05-22

Similar Documents

Publication Publication Date Title
US3627443A (en) Turbine blade
US3806274A (en) Gas turbine engine blades
US2807437A (en) Method for making intricate hollow powder metal parts
EP3429778B1 (en) Method of manufacturing advanced features in a core for casting
US6257831B1 (en) Cast airfoil structure with openings which do not require plugging
US7562691B2 (en) Core for turbomachine blades
US5337805A (en) Airfoil core trailing edge region
US3610769A (en) Porous facing attachment
US2510735A (en) Turbine element
US5536139A (en) Vortex flow blower having blades each formed by curved surface
JP2008142779A (en) Ceramic cores, methods of manufacture thereof and articles manufactured from the same
US20050247425A1 (en) Method and apparatus for determining the location of core-generated features in an investment casting
GB2042648A (en) Gas turbine engine hollow blades
GB2264755A (en) Stator blade construction
EP1321628A2 (en) Airfoil for a turbine nozzle of a gas turbine engine and method of making same
RU2726171C2 (en) Rod for gas turbine engine blade casting
US3707750A (en) Method for manufacturing a turbine blade
RU2004129949A (en) DEVICE FOR CASTING ELEMENT OF A GAS-TURBINE ENGINE (OPTIONS) AND A CASTING ROD FROM REFOSABLE METAL (OPTIONS)
US3370829A (en) Gas turbine blade construction
EP0663249B1 (en) Method for the production of ceramic shell moulds for casting with a lost mould
US4286924A (en) Rotor blade or stator vane for a gas turbine engine
US3263957A (en) Apparatus for the production of ceramic, cermet, and metal components
US3832847A (en) Regeneratively cooled rocket combustion chamber with slots between cooling channels
JP2002364304A (en) Turbine blade and method of manufacturing turbine blade
JP4327351B2 (en) Casting product, casting method and casting mold